A fuel burning method and a device for a gas turbine engine provides a nozzle (18) for leading a fluid to a combustion chamber arrangement downstream. The nozzle (18) comprises a body (406) with a centreline, a first channel along the centreline extending the body, and a nozzle tip (500) connected with a downstream end of the first channel and having a radius that extends from the center of the nozzle tip to the outer surface of the nozzle tip. The nozzle tip (500) comprises a downstream surface and a plurality of discharge passages, each discharge passages comprises an aperture defined in the downstream surface, wherein each aperture has an X, Y and Z axes, which are defined regarding a tangent, the radius and the centerline, each of the multiple discharge passages is located at an outlet angle of larger than 30 degrees, the outlet angle is measured regarding the respective Z-axis in a corresponding X-Z-plane.